1989 · 11 citations · 0 references
EngineeringAerospace EngineeringMechanical EngineeringAircraft DesignAircraft StructuresFlight MechanicsAircraft PerformanceClimb PerformanceFlight PerformanceFlat Plate SystemsHover PerformancePerformance Baseline AnalysisPerformance Baseline EstablishmentPerformance VerificationPerformance-based Baseline SettingPressure Altitude EffectsRotorcraft Climb Performance
Abstract : Testing was conducted to establish a performance baseline of the 12th year production UH-60A helicopter. A total of 19.5 productive hours were flown at two different test sites between 15 August and 2 September 1988. The performance of the 12th year production UH-60A Black Hawk was similar to or slightly degraded from the sixth year production UH-60A. At the primary mission gross weight, the performance met the requirement of the Prime Item Development Specification (PIDS). The out-of-ground effect hover gross weight capability was 17,416 pounds for 95 percent intermediate (30 minute limit) rated power available at 4000 feet pressure altitude and 35 C temperature. The vertical rate of climb of the 12th year aircraft exceeded the PIDS requirement by 21 ft/min. The 12th year production aircraft has an increase in equivalent flat plate area over the sixth year production aircraft. At 4000 ft pressure altitude, 35 C, and maximum continuous power, the cruise airspeed is 139 knots true airspeed, equal to the PIDS requirement.